Circuit for supplying fuel to an aeronautical cryogenic turbomachine and associated method
A fuel supply circuit for an aeronautical cryogenic turbomachine including: at least one cryogenic reservoir containing a liquid fuel topped with a boil-off gas and including a high-pressure liquid pump to supply at least one main propulsion device of the turbomachine with liquid fuel, an auxiliary turbomachine including an electric generator, a gas compressor to supply the auxiliary turbomachine with gaseous fuel, and a buffer gas reservoir connecting the gas compressor to the cryogenic reservoir to reinject gas into the cryogenic reservoir in order to maintain the pressure in the cryogenic reservoir above a predefined value, the electric generator supplying the high-pressure liquid pump and the gas compressor.
1. A fuel supply circuit for an aeronautical cryogenic turbomachine including: at least one cryogenic reservoir containing a liquid fuel-topped with a boil-off gas and including a high-pressure liquid pump connected to an outlet of said cryogenic reservoir and intended to supply at least one main propulsion device of the turbomachine with liquid fuel, an auxiliary turbomachine including an electric generator and producing heat via its exhaust gases, a gas compressor mounted between the cryogenic reservoir and the auxiliary turbomachine to supply the auxiliary turbomachine with gaseous fuel, and a buffer gas reservoir connecting an outlet of the gas compressor to an inlet of the cryogenic reservoir to reinject gas into the cryogenic reservoir in order to maintain the pressure in the cryogenic reservoir above a predefined value, said electric generator supplying electrical energy to said high-pressure liquid pump and said gas compressor.
2. The fuel supply circuit as claimed in claim 1 , wherein the buffer gas reservoir is also connected to a gas duct connecting the cryogenic reservoir to the gas compressor to allow the starting of the auxiliary turbomachine from the buffer gas reservoir.
3. The fuel supply circuit as claimed in claim 1 , further including a first heat exchanger between the gaseous fuel at the outlet of the gas compressor and the exhaust gases of the auxiliary turbomachine.
4. A fuel supply circuit as claimed in claim 3 , wherein the gaseous fuel thus heated in the first heat exchanger is intended to be directed to the main propulsion device of the turbomachine to be mixed with the liquid fuel.
5. The fuel supply circuit as claimed in claim 1 , wherein it further includes a second heat exchanger between the liquid fuel at the outlet of the high-pressure liquid pump and the exhaust gases of the auxiliary turbomachine.
6. The fuel supply circuit as claimed in claim 1 , further including a channel connecting an outlet of the high-pressure liquid pump to an inlet of the cryogenic reservoir to reinject liquid into said cryogenic reservoir.
7. The fuel supply circuit as claimed in claim 1 , wherein said liquid fuel is liquid hydrogen.
8. An aeronautical cryogenic turbomachine including a fuel supply circuit as claimed in claim 1 .
9. An aircraft including at least one aeronautical cryogenic turbomachine as claimed in claim 8 .
10. A fuel supply method for an aeronautical cryogenic turbomachine wherein a high-pressure liquid pump connected to an outlet of a cryogenic reservoir containing a liquid fuel topped by a boil-off gas supplies liquid fuel to at least one main propulsion device of the turbomachine, an auxiliary turbomachine including an electric generator produces heat via its exhaust gases, a gas compressor mounted between the cryogenic reservoir and the auxiliary turbomachine supplies gaseous fuel to the auxiliary turbomachine, and a buffer gas reservoir connecting an outlet of the gas compressor to an inlet of the cryogenic reservoir reinjects gas into the cryogenic reservoir in order to maintain the pressure in the cryogenic reservoir above a predefined value, said electric generator supplying electrical energy to said high-pressure liquid pump and said gas compressor.
11. The fuel supply method as claimed in claim 10 , wherein the electric generator also supplies electrical energy to non-propulsive power consumption sources.
12. The fuel supply circuit as claimed in claim 2 , further including a first heat exchanger between the gaseous fuel at the outlet of the gas compressor and the exhaust gases of the auxiliary turbomachine.
13. The fuel supply circuit as claimed in claim 2 , wherein it further includes a second heat exchanger between the liquid fuel at the outlet of the high-pressure liquid pump and the exhaust gases of the auxiliary turbomachine.
14. The fuel supply circuit as claimed in claim 2 , further including a channel connecting an outlet of the high-pressure liquid pump to an inlet of the cryogenic reservoir to reinject liquid into said cryogenic reservoir.
15. The fuel supply circuit as claimed in claim 3 , further including a channel connecting an outlet of the high-pressure liquid pump to an inlet of the cryogenic reservoir to reinject liquid into said cryogenic reservoir.
16. The fuel supply circuit as claimed in claim 4 , further including a channel connecting an outlet of the high-pressure liquid pump to an inlet of the cryogenic reservoir to reinject liquid into said cryogenic reservoir.
17. The fuel supply circuit as claimed in claim 5 , further including a channel connecting an outlet of the high-pressure liquid pump to an inlet of the cryogenic reservoir to reinject liquid into said cryogenic reservoir.
18. The fuel supply circuit as claimed in claim 2 , wherein said liquid fuel is liquid hydrogen.
19. The fuel supply circuit as claimed in claim 3 , wherein said liquid fuel is liquid hydrogen.
20. The fuel supply circuit as claimed in claim 4 , wherein said liquid fuel is liquid hydrogen.